introduccion al SRM ATR72

ATR42-400/500 - STRUCTURAL REPAIR MANUAL

INTRODUCTION Page 1

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INTRODUCTION

1. General Policy

A. GeneralThis manual is in conformity with the Air Transport Association Specificationnumber 2200 (ATA iSpec 2200). It provides descriptive information, instructionsand specific data relative to the repair of the ATR structure.It contains damage acceptability criteria, the identification of structurematerials and repair data applicable to the structural elements that are themost exposed to damage. It gives information on the standard repair procedures.All the data contained in this manual are approved by the authorities.The Structural Repair Manual is completed by the Illustrated Parts Catalog(IPC) which gives the list of replaceable structural elements.The Structural Repair Manual is laid out as follows:

Chapter 51 : Aeronautical standards, standard practices, materials andgeneral information on repairs

Chapters 52 through 57 : Specific structural chapters

The chapter numbers indicate an entire zone of the aircraft (for example :fuselage, wing, etc...), the section numbers indicate a sub-division of thiszone (for example : fuselage nose section, wing center box), and the subjectnumbers indicate a component of this zone (for example : FWD pressure bulkhead,front spar, etc...) (See para. 4.A.).To obtain a separation of the topics, the following block pages are used :

Description

Identification Figure

Allowable Damages

Repair

The Documentary Units (DU) are independently numbered and all the DU begin ona recto page. One page "PAGE LEFT BLANK INTENTIONALLY" is inserted if the DUfinishes on a recto page.The LEP records all the DU and their interval of pages.After a revision, if a DU has an added or deleted pages, all the pages of theDU are numbered.

B. List of Effective PagesAs noticed here-above the LEP records all the DUs and their interval of pages.It gives an overview of the parts revised.N, R or D indicates parts which are New, Revised or Deleted respectively.

C. Manual ValidityManual designated as ATR42-400/500 series SRM (this manual) covers theATR42-400/500 A/C -400, -500 series. This manual also covers ATR42-600designation.


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D. Data effectivityData that has no effectivity designation shall be applicable to all theaircraft series covered by this manual. Effectivity designations are used todefine the variants between the aircraft.Effectivity is expressed by MODIFICATION NUMBERS indicated :

In the block effectivity at the top of the variant Figures.

In the Identification Tables, in the - OBSERVATION MOD/SB REPAIR column, infront of each item variant.Example:Be. 3667T3724 ; Solution Before Modification 3667T3724Af. 3667T3724 ; Solution After Modification 3667T3724

In the Table of Contents, if a Configuration is created ('EFFEC' column)in front of each configuration ("a" or b on the AMTOSS code, see para.6.A.).Example :The required configuration is specified at the bottom of the pages. Themodifications concerned are given in the Table of Contents at the beginningof each ATA chapter.

The absence of modification number indicates commonality between all aircraft.The pages called "MODIFICATIONS/SERVICE BULLETINS LIST", placed - at thebeginning of the chapter, give the effectivity of each Modification Numberexpressed in Standard Version (ST) and by Manufacturer Serial Number (MSN).

NOTE : Before all investigation on structure Items make sure that the validityis correct (before or after Modification, Service Bulletin retrofitted,etc...).

E. Revision of the manualThe revision service is periodically provided. The revision is materialized bya "R" in the footer of the page. The latest revision date of the DU is shown inthe footer.The revised text is shown by a bar located in the left hand margin of thepages.The HIGHLIGHTS section (in the begin of the manual) records the revised DU andtheir reasons of revision.

F. Abbreviations used in the SRMThe abbreviations used in the SRM are recorded in the "LIST OF ABBREVIATIONS".

G. Symbols used in the repair drawingsIn order to simplify and clarify illustration of repair drawings, fastenersymbols are as follows :

SYMBOL TYPE

Existing fastener not affected by the repair


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SYMBOL TYPE

Existing fastener affected by the repair

Rivet

Blind fastener

Bolt

Countersunk fasteners (superimposed on other symbols)

Different diameters shall be represented by different symbols, as shown below:

TYPE SYMBOL

Rivet

Blind fastener

Bolt

2. General technical principles

A. DescriptionThis section is a brief description of the chapter concerned.

B. Identification FigureChapters 52 through 57 include the identification of the materials used inthe manufacture of the airplane. They indicate structural differences betweenairplanes of the same type which have been incorporated in production orretroactively, thus enabling the operator to identify the material of anysignificant component on any specific airplane in his fleet.Illustrations and text concerning the aircraft structure give description,material, and significant drawing numbers including appropriate assemblydrawing numbers. Where applicable, material information define the finishedheat treatment condition.

C. Allowable damageAllowable damage is damage that allows an operator to continue operatingan aircraft without any repairs other than local rework, and surface finishrestoration.


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NOTE : In the case of damage occurred on primary structure including PSE thatgo beyond SRM allowable limit, contact the manufacturer.

Wear Limits:Wear Limits on structural assemblies permit the assessment of in-service wearon single bolt and bolt-like parts, and also on attaching parts such as bearingand bushes. The limits are presented in tabular form in the Allowable Damagetopic of the appropriate manual section and indicate when rectification isrequired so that the assembly can continue satisfactorily in service.

D. Repair

(1) Definition of repairRepair instructions are intended to enable the operator to repair damageexceeding allowable damage limits.Several types of damage have been taken into account:

Metallic materials:Corrosion; cracks; scratches; dents; scores; gouges: nicks; abrasion;etc.

Non-metallic materials:Flaking; perforation; delamination; scratches; score; separation;denting; etc.

The repair approach shown in the flowchart (Refer to Description510001-03-001-A01) has to be followed

NOTE : In case of damage occurred in the areas where the structure is notregular, or joined with other components, and if any proximitycriteria is defined in the concerned repair procedure, contact themanufacturer.There is not limit to the number of applications of a repairprinciple unless otherwise specified in the instructions, andprovided that the geometry of the structure so permits. If damageoccurred is closed to an existing repair, contact the manufacturer.

(2) Recommendations of repair

WARNING : IF THE REPAIR IS NOT LIMITED BY MAX. DIMENSION, THE SIZE ISDEFINED BY THE NUMBER OF FASTENERS SHOWN ON REPAIR SCHEME(SKETCH). PITCH AND EDGE MARGINS DEPEND ON FASTENER DIAMETERSWHEN THEY ARE NOT IMPOSED BY EXISTING STRUCTURE (REFER TO SRM51-25-02 (FIT CONDITIONS OF BOLTS (TORQUE))).IN SUCH A CASE, IT COULD BE NECESSARY TO REMOVE PART OF THECOMPONENT THAT IS GREATER THAN THE OCCURRED DAMAGED AREA ORMAKE A DISPLACED SPLICE IN ORDER TO APPLY THE PRINCIPLE OFREPAIR AS DEFINED.

1. REPAIR PROXIMITYIN CASE OF MULTIPLE SIMULTANEOUS OR SUCCESSIVE DAMAGES,APPLICATION OF REPAIR PRINCIPLES CAN BE PERFORMED IF DAMAGE


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PROXIMITY CRITERIA AND GEOMETRY REQUESTED BY LEVEL OFREPAIRS IN THE CONCERNED REPAIR ARE MET.IN THE ABSENCE OF SPECIFIC CRITERIA, CONTACT THEMANUFACTURER.

2. REPAIR SHOWN IN THIS MANUAL ARE NOT APPLICABLE ON REPAIRSALREADY PERFORMED.

The repair application area is defined by precise structural references(frames, stringers, ribs, stiffeners, etc...).Repair schemes can be adapted to similar zones if:

Note is absent

Damage is similar.

Before all repairs, an inspection must be performed in order to accuratelydetermine extent of damage (Refer to SRM 51-00-01 (DEFECT/DAMAGEREPORTING)).Two kinds of repairs are defined:

Standard repairs and processes valid for all structure defined inchapter 51.

Specific repairs relevant to an element (or an area) and described inthe corresponding chapter or section.

Certain repairs are defined by means of graphs taking the following intoaccount:

type of damage

damage dimensions

damage area.

NOTE : When repair instructions are not available, this does not mean thatthe concerned structure is not repairable. Sometimes it is notpossible to give a standard repair, because the experience of in-service aircraft has not yet shown the necessity of such a repair.In certain cases an adapted repair design shall require anevaluation made by the aircraft manufacturer.As in-service experience shows the necessity, this manual shallbe procedures updated for repetitive and typical issue so as toinclude new repairs.In the possible case of serious damage the information of thismanual shall be completed by a direct link with a representative ofthe aircraft manufacturer support.

Temporary repairs, enabling limited service life are also defined incertain cases, and can be reported by a "TEMPORARY" in the title.When fatigue life of the repair is not stated in the repair principle,fatigue life has to be considered to be equal to the design life goal ofthe ATR which is 70000 cycles.Several solutions may be proposed for repairing given damage.In the case of cumulative damage, the repair must cover each type ofdamage.


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In the case where damage covers two areas, the repair retained will be theone corresponding to area comprising a flush criteria.

3. Repair Components Kit.For the components given in the REPAIR MATERIAL tables of repair schemes, referto "Index of Repair Drawing" or at the beginning of concerned chapter to check thedrawing number, its description, location and figure number to be able to order themanufactured parts.

4. How to use the manual

A. SRM Manual Breakdown Arrangement (Ref. Fig. 1)

B. Identification Figure

IDENTIFICATION FIGURE (Ref. Fig. 2)

COLUMNS DESCRIPTION

1 ITEM: Structural part itemAll required items, shown on the appropriate illustration, are listedin this column, in sequential order, beginning with Item Number 1 andcontinuing in steps of 5 (5, 10, 15, etc.).Structural components fitted in the same portion with differenteffectivities will be identified with an item number followed by asuffix letter A, B, C, etc.

2 DESCRIPTION: Structural part descriptionThis column contains the exact description of structural componentshown in the appropriate illustrations.

3 PART NUMBERStructural components will be given a manufacturer part numberconsisting of twelve characters. In general, the "as drawn" partsare LH. Where necessary, three additional characters are given forsymmetrical item (RH item). If available, the appropriate standard(production methods) will be given here (Ref. Fig. 5 Sheet 1).

4 MAT SPEC TREATMENT: Material and treatment of structure partsMaterial specification for metallic and/or non metallic components(Refer to SRM 51-30-00 (MATERIALS, ALTERNATIVES AND EQUIVALENTS -GENERAL)) are listed in this column. Complicated composite componentsare identified in detail by number of plies, material thickness and plydirection given in an appropriate table in the figure.


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COLUMNS DESCRIPTION

5 INTERCHANGEABILITY "IC"In the column is shown the interchangeability condition of a component(P/N).The interchangeability condition of concerned component is defined withone of following code numbers:

01: One way InterchangeabilityStates that the post MOD item can be used to replace a pre MOD itemwithout special action being required (not vice versa).

02: Two way InterchangeabilityEither the post MOD or pre MOD items can be used.

03: No InterchangeabilityThe basic item and post MOD item are not interchangeable.

6 THK mm (in): Thickness of structural componentWhere necessary, information concerning the thickness of sheet metalcomponent will be given in this column. The US/Imperial conversion(based on 1 in. = 25.4 mm) will be given in brackets. For machinedmetallic parts with variable thickness and composite materials,thicknesses are given by appropriate tables.

7 OBSERVATIONS MOD/SB/REPAIRInformation regarding the status "Before Modification" or "AfterModification" or "Before or After Service Bulletin" shall appear inthis column.A prefix letter shall be applied for Before/After/Mod/SB statement asfollows:

Be. = Before SB/Mod.

Af. = After SB/Mod.

In this column, the reference to a repair is given. The followingindications may be used:

For repair, see Pages REPAIR or

For repair, see XX-XX-XX Pages REPAIR

following the cases (XX-XX-XX for existing specific or general repairsChapter/Section/Subject Number is inserted).Where no repair exists, the space is left blank. Should a repair berequired and no information is given, a request must be sent to:ATR Structure Department1, Alle Pierre Nadot31712 BLAGNAC CedexFRANCEFax: + 33(0)562216290E-mail: [email protected]


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COLUMNS DESCRIPTION

8 ASSY DWGDrawings used for store issue of structural component.

C. Allowable Damage (Ref. Fig. 3)The allowable damage procedure gives the related data applicable to theconcerned area.

D. RepairThe repair procedure includes two parts:

1. the "JOB SET-UP INFORMATION" topic that gives all the information necessaryto do the repair.This topic has the tables that follows:

NOTE : Only the tables applicable to the Repair are in the repair

TABLE DESCRIPTION

REPAIR MATERIAL LIST This table records the repair material used to do theprocedure.The materials are associated with a reference to therelevant chapter 51 for the standard procedure

MATERIALS/CONSUMABLELIST

This table records the consumable used to do theprocedure.The consumable are associated with a reference to therelevant chapter 51 for the standard procedure

TOOLS LIST This table records the specific tool used to do theprocedure.

REFERENCED INFORMATION This table records the referenced information used todo the procedure.

2. The "PROCEDURE" topic that gives all the instructions to do the repair.The PROCEDURE topic is structured in subtask.

E. AMTOSS NumberingThe AMTOSS part numbers has a standard structure (Ref. Fig. 4)

5. Part Number Specification

A. Structure of A/C Manufacturer Part Number(Ref. Fig. 5)Suffix added to comply with manufacturing or spares requirements with thepurpose of a more detailed definition not specified in the Drawing.The allocation of suffixes between Product Support and engineering/Manufacturing is as follows:


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B. FOR CHAPTERS 52, 53 AND 55

SUFFIXES DEFINITION REMARKS

00 Part to drawing 00 = Part produced according to drawing

01 to 055051

Production Part notto drawing

01 = Part with pilot hole 2.5 mm dia. (3/32 in.)as specified on drawing02 = Undrilled part03 = Increased perimeter and finished holes04 = Increased perimeter and pilot holes05 = Increased perimeter and not drilled06 = Assy similar to drawing, but with differentcomposition

50 = Identical to drawing

51 = Special specification

60 to 89 Spare Part not todrawing and notstockable

99 Spare Part to drawingand not stockable

Numbering required for Product Support Breakout,but not applicable to production.

NOTE : Several suffixes are used by Spare Department to manufacture special P/N. and not as partially manufactured to allow the installation in theconstruction process. referring some diversion from the manufactured one.

NOTE : Means that for production needs the assy has to be manufacturedwith less or more components installed. The components not installedmay be furnished to the customer separately.

C. FOR CHAPTERS 54 AND 57

NOTE : For ATA Chapters 54 and 57, the delivery status of spare parts, notto drawing, is not univocally identified by suffix. In this case thedesired delivery condition must be clearly mentioned on the part order(e.g. "UNDRILLED", "WITH PILOT HOLES", etc.).

6. ATA iSpec 2200 Changes and CrossReferences Table Between Before and AfterConversion

ATR Structural Repair Manual Conversion has been provided in order to switch fromthe old ATA100 specification to the new iSpec 2200 specification.

ATR SRM Conversion is effective starting from June 2013 revision.

A. The Main Changement are:


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1. Old task numbers (example: chapter 530000 Figure 437) are not usedanymore. AMTOSS Code are the unique references which have to be used(example: 530000300837A01).

2. Allowable damages are numbered 200 in the AMTOSS Code (and not either 300 asbefore).

3. Repairs are numbered 300 in the AMTOSS Code (and not either 400 as before).

B. CrossReferences Table Between Before and After Conversion

In order to facilitate the research of a task with different reference beforeand after the Conversion, a cross-reference table is provided. The tablesincludes the allowable damages and the repair procedures introduced in themanual until February 2013 revision.

CHAPTER 52

Table 6: ALLOWABLE DAMAGEBefore

ConversionAfter Conversion Title After Conversion

(Refer to Damages521100-200-801-A01)

AFT PASSENGER/CREW DOOR


AFT PASSENGER/CREW DOOR ALLOWABLESCRATCHES, SCORES AND ABRASIONS


AFT PASSENGER/CREW DOORALLOWABLE SCRATCHES IN

MACHINED AND EXTRUDED PARTS

521100Fig 301


AFT PASSENGER/CREW DOOR ALLOWABLEDENTS IN SKIN PANELS (DE)

521100Fig 302


AFT PASSENGER/CREW DOOR SHOOT BOLT

521100Fig 303


AFT PASSENGER/CREW DOORCOUNTERBALANCE SPRINGS



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BeforeConversion

After Conversion Title After Conversion


PASSENGER COMPARTMENTEMERGENCY EXIT


PASSENGER COMPARTMENTEMERGENCY EXIT ALLOWABLE

SCRATCHES, SCORES AND ABRASIONS


PASSENGER COMPARTMENT EMERGENCYEXIT ALLOWABLE SCRATCHES INMACHINED AND EXTRUDED PARTS

522100Fig 301


PASSENGER COMPARTMENTEMERGENCY EXIT ALLOWABLEDENTS IN SKIN PANELS (DE)


FLIGHT COMPARTMENT OVERHEAD HATCH


FLIGHT COMPARTMENT OVERHEADHATCH ALLOWABLE SCRATCHES,

SCORES AND ABRASIONS


FLIGHT COMPARTMENT OVERHEADHATCH ALLOWABLE SCRATCHES INMACHINED AND EXTRUDED PARTS

522200Fig 301


FLIGHT COMPARTMENT OVERHEADHATCH ALLOWABLE DENTSIN SKIN PANELS (DE)


CARGO COMPARTMENT DOOR


CARGO COMPARTMENT DOOR ALLOWABLESCRATCHES, SCORES AND ABRASIONS


CARGO COMPARTMENT DOORALLOWABLE SCRATCHES IN


523100Fig 301


CARGO COMPARTMENT DOOR ALLOWABLEDENTS IN SKIN PANELS (DE)

523100Fig 302


CARGO DOOR HINGES(FUSELAGE AND DOOR SIDE)


SERVICE DOOR


SERVICE DOOR ALLOWABLESCRATCHES, SCORES AND ABRASIONS


SERVICE DOOR ALLOWABLE SCRATCHESIN MACHINED AND EXTRUDED PARTS

524200Fig 301


SERVICE DOOR ALLOWABLEDENTS IN SKIN PANELS (DE)

524200Fig 302


SERVICE DOOR SHOOT BOLT



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528200Fig 301


NLG AFT DOORS

Table 7: REPAIRBefore


520000Fig 401

(Refer to Repair520000-300-801-A01)

REPAIR SCHEME FOR HOLE FILLINGBY FASTENER ON THE DOORS SKIN

521100Fig 401


AFT PASSENGER/CREW DOOR SHOOT BOLT SURFACE REPAIR

521100Fig 402


AFT PASSENGER/CREW DOOR FWD BTM INTERNAL REPAIR

521100Fig 403


AFT PASSENGER/CREW DOOR AFT BTM INTERNAL REPAIR

521100Fig 404


AFT PASSENGER/CREW DOOR BOTTOM INTERNAL REPAIR

521100Fig 405


AFT PASSENGER/CREW DOOR REPAIRSCHEME FOR INNER SKIN TOP AFT

521100Fig 406


AFT PASSENGER/CREW DOOR REPAIR SCHEME FOR INNERSKIN FWD UPPER SIDE

521100Fig 407


AFT PASSENGER/CREW DOOR REPAIR SCHEME FOR INNERSKIN FWD UPPER SIDE

521100Fig 408


AFT PASSENGER/CREW DOOR CRACK REPAIR LAST STEP FWDSEMI AUTOMATIC HANDRAIL

521100Fig 409


AFT PASSENGER CREW DOOR- INTERMEDIATE STEPS FWDAND AFT - CRACK REPAIR

522100Fig 401


PASSENGER COMPARTMENT EMERGENCYEXIT LOCALIZED DENT - SKINREPAIR BY EXTERNAL PATCH

523100Fig 401


CARGO COMPARTMENTDOOR PAN REPAIR

523100Fig 402


CARGO COMPARTMENT DOOR FITTINGFOR LOWERING ARTICULATION POINT

523100Fig 403


REPAIR SCHEME FORINTERCOSTAL REPAIR-CARGODOOR STA6250, STA6174

523100Fig 404


REPAIR SCHEME FORINTERCOSTAL REPAIR-CARGO DOOR

523100Fig 405


REPAIR SCHEME FOR CARGO DOOR PANREPAIR AT STRUT FITTING LOCATION



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BeforeConversion


523100Fig 406


REPAIR SCHEME FOR CARGO DOOR PANREPAIR AT STRUT FITTING LOCATION

523100Fig 407


REPAIR SCHEME FORINTERCOSTAL REPAIR-CARGO DOOR

523100Fig 408


CARGO COMPARTMENT DOORREPAIR SCHEME FOR INTERCOSTAL

REPAIR STA6174, STA6250

523100Fig 409


CARGO COMPARTMENT DOORREPAIR SCHEME FOR INTERCOSTALREPAIR STA6434.75, STA6619.5,STA6695.5, STA7065, STA7141

523100Fig 410


CARGO COMPARTMENT DOOR - PANREPAIR - ACTUATOR FITTING AREA

524100Fig 401


REPAIR SCHEME FOR AFTACCESS DOOR SKIN AT FRAME 45

524200Fig 401


SERVICE DOOR SHOOT BOLTSURFACE REPAIR (STEP BY STEP)

524200Fig 402


SERVICE DOOR PANREPAIR ON FWD BTM SIDE

524200Fig 403


SERVICE DOOR PANREPAIR ON AFT BOTTOM SIDE

524200Fig 404


SERVICE DOOR PANREPAIR ON AFT BOTTOM SIDE

524200Fig 405


SERVICE DOOR - REPAIRSCHEME FOR SERVICE DOOR

LOWER FRONT AND REAR CORNER

524200Fig 406


SERVICE DOOR REPAIR SCHEME FORDAMAGED SKIN AT DOOR HINGE AREA

528100Fig 401


MLG DOORS METALLICSANDWICH PANELS REPAIR

528100Fig 402


MLG DOOR REPAIRSCHEME FOR DAMAGE DOORREAR EDGE (OBSOLETE)

528100Fig 403


MLG DOOR REPAIR SCHEME FORDEBONDING ON FOLDING DOOR EDGE

528100Fig 404


MLG DOOR REPAIR SCHEMEEDGE SKIN DEBONDING

528100Fig 405


MLG DOOR OUTER SKINREPAIR (LH/RH SIDE)

528100Fig 406


MLG CORROSION REPAIR UNDERSEAL RETAINER (LH/RH)

528200Fig 401


NLG DOORS REPAIR ANDREINFORCEMENT OF THE

ANGLES OF AFT NLG DOORS



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528200Fig 402


NLG DOORS REPAIR SCHEMEFOR AFT DOOR CORE SKIN DEBOND

528200Fig 403


NLG DOORS REPAIR SCHEMEFOR DAMAGED AFT DOOR

528200Fig 404


REPAIR SCHEME TO REPLACETHE BUSHING OF AFT NLG

DOOR HINGE FITTING (LH/RH)

CHAPTER 53



530000Fig 301


CARGO AREA FLOOR PANEL

530000Fig 302


AISLE, ENTRY DOOR ANDTOILET AREA FLOOR PANEL

530000Fig 303


UNDER SEAT AREA FLOOR PANEL

530000Fig 304


FUSELAGE STRUCTURE SEAT TRACK

530000Fig 305


FUSELAGE STRUCTURE FLOOR BEAM

530000Fig 306


FUSELAGE FLOOR PANELS ATTACHMENTWITH SEAT TRACKS AND FLOORBEAMS (FROM FRAME 13 TO 39)- ALLOWABLE MISSING FASTENERS


FUSELAGE NOSE SECTION STRUCTURE


FUSELAGE NOSE SECTIONSTRUCTURE ALLOWABLE



FUSELAGE NOSE SECTION STRUCTURE ALLOWABLE SCRATCHES,SCORES AND ABRASIONS INPRESSURIZED BULKHEADS


FUSELAGE NOSE SECTION STRUCTURE ALLOWABLE SCRATCHES IN


531100Fig 301


FUSELAGE NOSE SECTION STRUCTURE ALLOWABLE DENTS IN SKINPANELS (VALID FOR DE)

531100Fig 302


FUSELAGE NOSE SECTION STRUCTURE STATIC AREA (LH AND RH)



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FUSELAGE FWD SECTION STRUCTURE


FUSELAGE FWD SECTION STRUCTURE ALLOWABLE SCRATCHES,SCORES AND ABRASIONS


FUSELAGE FWD SECTION STRUCTURE ALLOWABLE SCRATCHES IN



FUSELAGE FWD SECTION STRUCTURE ALLOWABLE DENTS IN SKINPANELS (VALID FOR DE)


FUSELAGE FWD SECTION STRUCTURE WINDOW FRAME ALLOWABLE DAMAGES

533100Fig 301


FUSELAGE FWD SECTIONSTRUCTURE SEAT TRACK ANDFLOOR BEAM ALLOWABLE

DAMAGES REFERENCE CHAPTERS

533181Fig 301


ICE SHIELD LH/RH


FUSELAGE CENTER SECTION STRUCTURE


FUSELAGE CENTER SECTIONSTRUCTURE ALLOWABLE



FUSELAGE CENTER SECTION STRUCTURE ALLOWABLE SCRATCHES, SCORES ANDABRASIONS IN PRESSURIZED BULKHEAD


FUSELAGE CENTER SECTION STRUCTURE ALLOWABLE SCRATCHES IN



FUSELAGE CENTER SECTIONSTRUCTURE ALLOWABLE

DENTS IN SKIN PANELS (DE)


FUSELAGE CENTER SECTION STRUCTURE WINDOW FRAME ALLOWABLE DAMAGES

535100Fig 301


FUSELAGE CENTER SECTIONSTRUCTURE SEAT TRACK ANDFLOOR BEAM ALLOWABLE


535730Fig 301


MLG ATTACH FITTINGS - LH/RH

536100Fig 301


FUSELAGE REAR CENTER SECTIONSTRUCTURE ALLOWABLE DAMAGES



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BeforeConversion



FUSELAGE REAR CENTER SECTIONSTRUCTURE ALLOWABLE



FUSELAGE REAR CENTER SECTIONSTRUCTURE ALLOWABLE SCRATCHES,

SCORES AND ABRASIONS INTOILET AND SERVICE POINT AREAS


FUSELAGE REAR CENTER SECTIONSTRUCTURE ALLOWABLE SCRATCHESIN MACHINED AND EXTRUDED PARTS


FUSELAGE REAR SECTIONSTRUCTURE ALLOWABLE



FUSELAGE REAR SECTION STRUCTURE WINDOW FRAMES ALLOWABLE DAMAGES


FUSELAGE REAR SECTIONSTRUCTURE ALLOWABLE



FUSELAGE TAIL SECTION STRUCTURE


FUSELAGE TAIL SECTIONSTRUCTURE ALLOWABLE



FUSELAGE TAIL SECTION STRUCTURE ALLOWABLE SCRATCHES, SCORES ANDABRASIONS IN PRESSURIZED BULKHEAD


FUSELAGE TAIL SECTION STRUCTURE ALLOWABLE SCRATCHES IN


538100Fig 301


FUSELAGE TAIL SECTIONSTRUCTURE ALLOWABLE


539100Fig 301


RADOME, MLG FAIRINGAND TAIL CONE AREAS

539120Fig 301


LANDING LIGHT TRANSPARENT COVER

539122Fig 301


FAIRING SKIN PANELS

539124Fig 301


STROBO LIGHT TRANSPARENT COVER



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530000Fig 401


FUSELAGE SKIN - REPAIRSCHEME FOR ELONGATED

HOLES BY SHOULDER BUSHING

530000Fig 402


FUSELAGE SKIN - SMALLDAMAGE/EXTERNAL REPAIR

530000Fig 403


FUSELAGE SKIN - SMALLDAMAGE/FLUSH REPAIR

530000Fig 404


FUSELAGE SKIN - BETWEENSTRINGERS/EXTERNAL REPAIR

530000Fig 405


FUSELAGE SKIN - BETWEENSTRINGERS/FLUSH REPAIR

530000Fig 406


FUSELAGE SKIN - ATSTRINGER/EXTERNAL REPAIR

530000Fig 407


FUSELAGE SKIN - ATSTRINGER/FLUSH REPAIR

530000Fig 408


FUSELAGE SKIN - AT FRAME (WITHSKIN PAD)/EXTERNAL REPAIR

530000Fig 409


FUSELAGE SKIN - AT FRAME (WITHOUTSKIN PAD)/EXTERNAL REPAIR

530000Fig 410


FUSELAGE SKIN - AT FRAME(WITHOUT SKIN PAD)/FLUSH REPAIR

530000Fig 411X


FUSELAGE SKIN - ATSTRINGER/TEMPORARY REPAIR

530000Fig 412


FUSELAGE SKIN - AT STRINGERLOCATION/EXTERNAL REPAIR(TEMPORARY TO PERMANENT)

530000Fig 413


FUSELAGE SKIN - AT STRINGERLOCATION/FLUSH REPAIR

(TEMPORARY TO PERMANENT)

530000Fig 414


FUSELAGE FRAME -INNER FLANGE REPAIR

530000Fig 415


FUSELAGE FRAME -OUTER FLANGE REPAIR

530000Fig 416


FUSELAGE FRAME - HEAVYDAMAGE FLANGE REPAIR

530000Fig 417


FUSELAGE FRAME - FAILSAFE ANGLE REPAIR

530000Fig 418


FUSELAGE SEAT TRACK -REPAIR (UPPER HORIZONTAL

FLANGE REPLACEMENT)

530000Fig 419


FUSELAGE SEAT TRACK -REPAIR (UPPER HORIZONTALFLANGE + WEB REPLACEMENT)



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BeforeConversion


530000Fig 420


FUSELAGE SKIN - LONGITUDINALLAP JOINT BETWEEN FRAMES

(BOTH SKINS ENDSDAMAGED)/EXTERNAL REPAIR

530000Fig 421


FUSELAGE SKIN - LONGITUDINAL LAPJOINT BETWEEN FRAMES/FLUSH REPAIR

530000Fig 422


FUSELAGE SKIN - AT FRAME(WITH SKIN PAD)/FLUSH REPAIR

530000Fig 423


FUSELAGE SKIN - REPAIR SCHEMEFOR UPPER AND LOWER SKINSAT LONGITUDINAL LAP JOINTAND FRAMES/EXTERNAL REPAIR

530000Fig 424


FUSELAGE SKIN - REPAIRSCHEME FOR UPPER SKIN ATLONGITUDINAL LAP JOINT

BETWEEN FRAMES/EXTERNAL REPAIR

530000Fig 425


FUSELAGE STRINGER -FORMED STRINGER REPAIR

530000Fig 426


FUSELAGE STRINGER - EXTRUSIONSTRINGER OUTSIDE SPECIALSTGR4 AND STGR5 REPAIR

530000Fig 427


FUSELAGE STRINGER - TYPICALEXTRUDED STRINGER REPAIR

530000Fig 428


FUSELAGE FLOOR BEAM -FLOOR CROSS BEAM REPAIR

530000Fig 429


FUSELAGE CREASEBEAM - REPAIR SCHEME

530000Fig 430


FUSELAGE SKIN - REPAIRSCHEME SKIN FOR HOLEWITH EXTERNAL DOUBLER

530000Fig 431


FUSELAGE SKIN - REPAIR SCHEME FORSKIN HOLE WITH INTERNAL DOUBLER

530000Fig 432


FUSELAGE SEAT TRACK -REPAIR SCHEME FOR SPLICING

530000Fig 433


FUSELAGE FRAME - REPAIRSCHEME FOR LOWER FR13 TOFR34 BETWEEN STGR17 LH/RH

530000Fig 434


FUSELAGE FRAME - REPAIRSCHEME FOR CORROSION ON

FRAMES BETWEEN STGR17 LH/RH

530000Fig 435


FUSELAGE SKIN - REPAIR SCHEMEFOR HOLE FILLING BY FASTENER

530000Fig 436


FUSELAGE FLOOR BEAM -FRAMES/REPAIR SCHEMEFOR FLOOR BEAM SPLICE



R Oct 01/14

BeforeConversion



Replaced by DWG S530R0022 issue B

FUSELAGE FLOOR BEAM - FRAMES/REPAIR SCHEME FOR FLOOR BEAM

SPLICE AT SEAT TRACK - (OBSOLETE)530000Fig 437


FUSELAGE FLOOR BEAM - SPLICINGPRINCIPLE AT SEAT TRACK (RH SIDE)


FUSELAGE COMPOSITE -BONDED STRUCTURE FIBRELAMSANDWICH PANEL REPAIR530000

Fig 438(Refer to Repair

530000-300-839-A01)FUSELAGE COMPOSITE -

SUPERFICIAL DAMAGE REPAIR

530000Fig 439


FUSELAGE COMPOSITE -IDENTATION CAUSING DAMAGETO BOTH SKIN AND CORE

530000Fig 440


FUSELAGE COMPOSITE -DELAMINATION REPAIR

530000Fig 441


FUSELAGE COMPOSITE - FIBRELAMSANDWICH PANEL INSERT REMOVAL

530000Fig 442


FUSELAGE FLOOR BEAM -REPAIR SCHEME - FOR SPLICE

AT SEAT TRACK RUN-OUT

530000Fig 443


FUSELAGE SEAT TRACK -REPAIR SCHEME FOR SEAT

TRACK TO FLOOR BEAM JOINT

530000Fig 444


FUSELAGE FRAME - REPAIR SCHEMEFOR FRAME FAIL SAFE ANGLESPLICE (PRINCIPLE BETWEENTWO ADJACENT STRINGERS)

530000Fig 445


FUSELAGE FRAME - LWR FRAMEINNER FLANGE SPLICING (FOR

PARTIAL REPLACEMENT OF FRAME)AT STRINGER LEVEL - (OBSOLETE)

530000Fig 446


FUSELAGE COMPOSITE - REPAIRSCHEME TO INSTALL INSERT NTA12151OR NTA12150 ON THE FLOOR PANELWITH MISALIGNED/ELONGATED HOLE

530000Fig 447


FUSELAGE STRINGER -BONDED STRINGER/REPAIRBY STRINGER SPLICE

530000Fig 448


FUSELAGE STRINGER - BONDEDSTRINGER/DE-BONDED REPAIR

530000Fig 449


FUSELAGE FLOOR BEAM - REPAIRSCHEME FOR UPPER AND LOWERFLANGE (APPLICABLE TO FLOORBEAM MADE FROM NTA44770)



R Oct 01/14

BeforeConversion


530000Fig 450


FUSELAGE COLD WORKED HOLE -REPAIR SCHEME FOR FILLING BYFASTENER ON FUSELAGE FORMED

FRAMES, STRINGERS, SEAT, TRACKS,FLOOR BEAMS AND STIFFENERS


FUSELAGE CREASE BEAM - SPLICINGPRINCIPLE OF INNER CHORD AT FR19





530000Fig 451


FUSELAGE CREASE BEAM - SPLICINGPRINCIPLE OF INNER CHORDAT FR31 OR FR32 OR FR33

530000Fig 452


FUSELAGE FLOOR BEAM -SPLICING PRINCIPLE AT STATION

STA6427.3, STA6887.7,STA7348, STA10076 AND STA15959

530000Fig 453


FUSELAGE SEAT TRACK -REPAIR SCHEME FOR SEAT TRACK

SPLICING AT FLOOR BEAM

530000Fig 454


FUSELAGE FLOOR BEAM - SPLICINGPRINCIPLE AT FR36 NEAR BL0

530000Fig 455


FUSELAGE FLOOR BEAM -SPLICING PRINCIPLE AT FR36

531100Fig 401


REPAIR SCHEME FORFUSELAGE SKIN/OIL CANNING

531110Fig 401


REPAIR SCHEME FOR DAMAGEDWEB CHORD AND SPLICE PLATE

531110Fig 402


REPAIR SCHEME FOR DAMAGEDBULKHEAD CHORD BETWEEN

BL0 AND BL475 - LH/RH SIDE

531110Fig 403


REPAIR SCHEME FOR BURN FR1 WEB

531110Fig 404


REPAIR SCHEME FOR DAMAGEDFR1 WEB AT STA2962

531110Fig 405


REPAIR BULKHEADSTIFFENERS CORROSION

531110Fig 406


LOWER WEB FRAME 1CORROSION REPAIR (LH/RH)BETWEEN BL187.5 AND BL350

531124Fig 401


REPAIR SCHEME FOR DAMAGEDSKIN BETWEEN FR5 AND FR6 ANDFROM WL2327.5 TO WL2640.4



R Oct 01/14

BeforeConversion


531128Fig 401


REPAIR SCHEME FOR LOWERPANEL AT FR9 AND BETWEEN

STGR11 AND STGR12A

531128Fig 402


REPAIR SCHEME FOR SKIN CORROSIONAT DME 2 ANTENNA LOCATION

531128Fig 403

(Refer to Repair531128-300-802-B01)

REPAIR SCHEME FOR SKIN CORROSIONAT DME 2 ANTENNA LOCATION

531128Fig 405


RH LOWER AFT PANEL -REPAIR GROUND POWER BOX

531128Fig 406


RH LOWER AFT PANEL -DOUBLER FOR EXTERNAL DCPOWER RECEPTACLE REPAIR

531128Fig 407


RH LOWER AFT PANEL -POWER BOX CRACK REPAIR

531128Fig 408


RH LOWER AFT SKIN PANEL REPAIRBETWEEN FR7 AND FR8 AT BL800

531131Fig 401


REPAIR SCHEME FOR CRACK OFLOWER SILL BETWEEN NODES 6/7

531140Fig 401


REPAIR SCHEME FOR DAMAGED TEEFLOOR BEAM SPLICE AT STA4426/FR7

531140Fig 402X


TEMPORARY REPAIR SCHEME FOR CRACKON LH/RH FRAME 5 AT STA3982.5

531140Fig 403


PERMANENT REPAIR SCHEME FORFUSELAGE FRAME 5 BETWEENSTGR11 AND NODE 6 (LH/RH)

533121Fig 401


CROWN PANEL - REPAIR SCHEMEFOR SKIN CORROSION AT ADF1 ANDADF2 ANTENNA LOCATION (COLLINS)

533126Fig 401


REPAIR SCHEME FOR FUSELAGE LOWERSKIN CORROSION BETWEEN FR19 ANDFR20 AT BL0 UNDER TCAS ANTENNA

533126Fig 402

New Repair moved from531128 Fig.404 to533126 Fig.402(Refer to Repair

533126-300-802-A01)

REPAIR SCHEME FOR SKIN CORROSIONAT DME1 ANTENNA LOCATION

533150Fig 401


CHORD CREASE BEAM REPAIR

533181Fig 401


REPAIRS FOR METALLIC ICE SHIELD

533300Fig 401


REPAIR SCHEME FORSEAT TRACK SPLICING

535140Fig 401


REPAIR SCHEME FOR CRACK ON FR26/STGR13 (LH/RH) - (OBSOLETE)



R Oct 01/14

BeforeConversion


535300Fig 401


SEAT TRACKS - REPAIR SCHEMEFOR SEAT TRACK SPLICING

535730Fig 401


REPAIR SCHEME FOR CORROSIONBLEND OUT ALLOWABLE DAMAGE ONTRUSS SHEAR MEMBER LUGS, F/S AND R/S MLG FITTINGS LUGSAND F/S AND R/S STRUTS LUGS


KEEL BEAM PLATE REPAIR LH/RH SIDE BETWEEN FRAME 25 AND

FRAME 27 AT STRINGER 21 (4 CASES)535770Fig 401


MLG BULKHEADS - KEEL BEAM PLATEREPAIR LH/RH BETWEEN FRAME 25 ANDFRAME 27 AT STRINGER 21 (4 CASES)

536125Fig 401


LH LATERAL LOWER PANEL - REPAIRSCHEME FOR PAX DOOR SURROUND SKINAT SHOOT BOLT LOCATION LH/RH SIDE

536140Fig 401


REPAIR SCHEME FOR FRAMES 30,31, 33 AND 34 SPLICING LH ANDRH BETWEEN STRINGERS 10 AND 11

536140Fig 402


REPAIR SCHEME FOR FLOOR BEAMREPLACEMENT BY SPLICE AT FRAME41 (STA19149) LH AND RH SIDE

536140Fig 403


REPAIR SCHEME FOR FRAME 36SPLICING LH AND RH AT STRINGER 18

536140Fig 404



536140Fig 405



536140Fig 406


FRAMES - STA17319/FR36 -REPAIR SCHEME FOR LOCAL

REINFORCEMENT BETWEEN STGR14AND STGR15 (RH/LH SIDE)

536140Fig 407


REPAIR SCHEME FOR LOWERFRAME 40 SPLICING BETWEENSTGR19 LH AND STGR19 RH

536140Fig 408


FLOOR BEAM CORROSION REPAIRAT STA19149/FR41 RH SIDE

536300Fig 401



536770Fig 401


FRAMES - STA17459/FR37 -REPAIR SCHEME FOR LOCALREINFORCEMENT BETWEEN

STGR14 AND STGR15 (RH SIDE)

538140Fig 401


FRAME - REPAIR SCHEME FOR A LIGHTCORROSION ON FRAME 44 (STA 20425)



R Oct 01/14

BeforeConversion


538140Fig 402


FRAME - REPAIR SCHEME FOR A HEAVYCORROSION ON FRAME 44 (STA 20425)

538300Fig 401



539121Fig 401


RADOME REPAIR

539121Fig 402


RADOME PAINTING


RADIO ELECTRIC INSPECTION539121Fig 403 (Refer to Repair

539121-300-804-A01)INSTALLATION OF LIGHTNINGPROTECTION AND INSPECTION

539122Fig 401


WING TO FUSELAGE FAIRINGSKIN PANELS - REPAIR

539142Fig 401


REPAIR SCHEME FOR FLANGERIB 29 LH AND RH SIDE

539143Fig 401


REPAIR SCHEME FOR MLG FAIRINGFRAME 27A (LH/RH) SMALLER DAMAGE

539143Fig 402


REPAIR SCHEME FOR MLGFAIRING FRAME 27A (LHAND RH) BIGGER DAMAGE

539180Fig 401


MISCELLANEOUS - MLGFAIRING RIB REPAIR

CHAPTER 54



541161Fig 301Config 1


TUBULAR MOUNT


(Refer to Damages541161-200-801-B01)

TUBULAR MOUNT



TUBULAR MOUNT



TUBULAR MOUNT



R Oct 01/14





REPAIR SCHEME FOR ASUPERFICIAL SMOOTHING

ON FORWARD TUBULAR MOUNT



REPAIR SCHEME FOR ASUPERFICIAL SMOOTHING

ON FORWARD TUBULAR MOUNT



REPAIR SCHEME FOR ACALIBRATED SMOOTHING ONFORWARD TUBULAR MOUNT



REPAIR SCHEME FOR ACALIBRATED SMOOTHING ONFORWARD TUBULAR MOUNT



ATTACH FITTINGS REPAIR SCHEMEFOR FWD BEAM ATTACHMENT JUNCTION

SHACKLE (ELONGATED HOLES)



ATTACH FITTINGS REPAIR SCHEMEFOR FWD BEAM ATTACHMENT JUNCTION

SHACKLE (ELONGATED HOLES)



COWLS AND FAIRINGS REPAIRSCHEME FOR DAMAGED COWL



COWLS AND FAIRINGS REPAIRSCHEME FOR DAMAGED COWL



COWLS AND FAIRINGS REPAIR SCHEME FOR CRACKSON OUTLET ASSY - AIR



COWLS AND FAIRINGS REPAIRSCHEME FOR CRACK ON AFT EDGING



COWLS AND FAIRINGS REPAIRSCHEME FOR CRACK ON AFT EDGING



OIL COOLER DUCT REPAIRSCHEME FOR CRACKS ON UPPERSURFACE AT ATTACHMENT HOLES



OIL COOLER DUCT REPAIR SCHEMEFOR CRACKS, CHIPPING AND

ELONGATION AT ATTACHMENT HOLES



OIL COOLER DUCT REPAIR SCHEMEFOR CRACKS ON UPPER SURFACE



R Oct 01/14

BeforeConversion




OIL COOLER DUCT REPAIR SCHEMEFOR CRACKS ON UPPER SURFACE



OIL COOLER DUCT REPAIR SCHEMEFOR WEARS ON UPPER SURFACE



COWL AND FAIRING REPAIRSCHEMES FOR CRACK ON UPPERCOWL AT CENTER CUT OUT



COWL AND FAIRING REPAIRSCHEMES FOR CRACK ON UPPER COWL



COWL AND FAIRING REPAIRSCHEMES FOR CRACK ON SKINOF UPPER COWL AT CORNER



COWL AND FAIRING REPAIR SCHEMESFOR CRACK ON SKIN OF UPPER COWL



COWL AND FAIRING REPAIRSCHEMES FOR THE EDGINGCRACK ON UPPER COWL



COWL AND FAIRING REPAIRSCHEMES FOR THE EDGINGCRACK ON UPPER COWL



COWL AND FAIRING REPAIRSCHEME FOR UPPER COWLCOMPONENTS REPLACEMENT



COWL AND FAIRING REPAIRSCHEME FOR UPPER COWLCOMPONENTS REPLACEMENT



REPAIR SCHEME FOR A SUPERFICIALSMOOTHING ON REAR TUBULAR MOUNT



REPAIR SCHEME FOR A SUPERFICIALSMOOTHING ON REAR TUBULAR MOUNT



REPAIR SCHEME FOR A CALIBRATEDSMOOTHING ON REAR TUBULAR MOUNT



REPAIR SCHEME FOR A CALIBRATEDSMOOTHING ON REAR TUBULAR MOUNT



REPAIR SCHEME FOR DAMAGEDEDGE ON LATERAL PANEL



R Oct 01/14

BeforeConversion




REPAIR SCHEME FOR DAMAGEDEDGE ON LATERAL PANEL



REPAIR SCHEME FOR CRACK ONFIREWALL DEFINITION OF ZONES



REPAIR SCHEME FOR CRACK ONFIREWALL DEFINITION OF ZONES

542261Fig 403XConfig 1


TEMPORARY REPAIR SCHEME FORCRACK ON UPPER FIREWALL PANEL



TEMPORARY REPAIR SCHEME FORCRACK ON UPPER FIREWALL PANEL



REPAIR SCHEME FOR CRACKON REINFORCING ANGLE



TEMPORARY REPAIR SCHEME FORCRACK ON FRONT FIREWALL PANEL



TEMPORARY REPAIR SCHEME FORCRACK ON FRONT FIREWALL PANEL



REPAIR SCHEME FOR CRACKON FRONT FIREWALL PANEL



REPAIR SCHEME FOR CRACKON FRONT FIREWALL PANEL



REPAIR SCHEME FOR CRACKON UPPER FIREWALL PANEL



REPAIR SCHEME FOR CRACKON UPPER FIREWALL PANEL



REPAIR SCHEME FOR PERFORATIONON UPPER FIREWALL PANEL



REPAIR SCHEME FOR PERFORATIONON UPPER FIREWALL PANEL



REPAIR SCHEME FORCRACK ON FIREWALL PANEL



R Oct 01/14

BeforeConversion


543261Fig 401


FAIRING STRUCTURE - REPAIRSCHEME FOR DELAMINATION ON

LOWER SURFACE OF ENGINE NACELLE

CHAPTER 55





HORIZONTAL AND VERTICALSTABILIZER DAMAGE TYPEAND DEFECT DESCRIPTION

550000GENERALConfig 2


HORIZONTAL AND VERTICALSTABILIZER DAMAGE TYPEAND DEFECT DESCRIPTION

550000TABLE 1Config 2






C/E VERTICAL STABILIZER ALLOWABLE DAMAGE






C/E HORIZONTAL STABILIZER MULTISPAR BOX ALLOWABLE DAMAGES



C/E VERTICAL AND HORIZONTALSTABILIZER JOINTS ALLOWABLE DAMAGES



R Oct 01/14

BeforeConversion



















R Oct 01/14

BeforeConversion




HORIZONTAL STABILIZER SPAR BOX


HORIZONTAL STABILIZER SPAR BOX ALLOWABLE

SCRATCHES, SCORES AND ABRASION


HORIZONTAL STABILIZER SPARBOX ALLOWABLE SCRATCHES INMACHINED AND EXTRUDED PARTS


HORIZONTAL STABILIZER SPARBOX ALLOWABLE DENTS IN

SKIN PANELS (VALID FOR DE)

551100Fig 301


HORIZONTAL STABILIZER SPAR BOX ALLOWABLE DENTSIN HONEYCOMB SKIN PANEL

551100Fig 302Config1 and

Config 2


HORIZONTAL STABILIZER SPARBOX DAMAGE TYPES AND REPAIRS

551230Fig 301


HORIZONTAL STABILIZERLEADING EDGE SKIN PANELS

552000Fig 301


ELEVATOR AND TABS COMPOSITEPARTS - ALLOWABLE DAMAGE


VERTICAL STABILIZER SPAR BOX


VERTICAL STABILIZER SPARBOX ALLOWABLE SCRATCHES,

SCORES AND ABRASION


HORIZONTAL STABILIZER SPARBOX ALLOWABLE SCRATCHES INMACHINED AND EXTRUDED PARTS


VERTICAL STABILIZER SPARBOX ALLOWABLE DENTS INSKIN PANEL (VALID FOR DE)

553100Fig 301


VERTICAL STABILIZER SPAR BOX ALLOWABLE DENTSIN HONEYCOMB SKIN PANEL


Config 2


VERTICAL STABILIZER SPAR BOX FORIMPACT DAMAGES TYPES AND REPAIRS



R Oct 01/14

BeforeConversion


554000Fig 301


RUDDER COMPOSITEPART ALLOWABLE DAMAGE

554500Fig 301


RUDDER TAB



550000General


STABILIZERS GENERAL REPAIRS

550000Fig 401


STABILIZER GENERAL DEBONDED METALLIC SKIN

AND HONEYCOMB CORE REPAIR

550000Fig 402


REPAIR OF DAMAGE TO ONE METALLICSKIN AND HONEYCOMB CORE

550000Fig 403


REPAIR OF DAMAGE TO ONE METALLICSKIN AND HONEYCOMB CORE

550000Fig 404


REPAIR TO METALLIC SANDWICH PANEL

550000Fig 405


REPAIR OF DENTS IN METALHONEYCOMB STRUCTURE


RUDDER, ELEVATOR AND TABS GRAPHITE COMPOSITE STRUCTURE REPAIR PROCEDURE COMMONTO TYPICAL REPAIR FIGURE550000

Fig 406(Refer to Repair

550000-300-806-A01)

RUDDER, ELEVATOR AND TABS REPAIR A SEPARATION

SKIN CORE AND DELAMINATION

550000Fig 407


RUDDER, ELEVATOR AND TABS REPAIR B PERFORATINGAND NON PERFORATING DAMAGE

550000Fig 408


RUDDER, ELEVATOR AND TABS REPAIR C SANDWICH

STRUCTURE PERFORATING DAMAGE

550000Fig 409


RUDDER, ELEVATOR AND TABS REPAIR D1 AND REPAIR D2 SEPARATION SKIN CORE DAMAGE

550000Fig 410


RUDDER, ELEVATOR AND TABS REPAIR E1 AND REPAIR E2

PERFORATING DAMAGE SANDWICH ZONE

550000Fig 411


RUDDER, ELEVATOR ANDTABS REPAIR F DENTON SANDWICH STRUCTURE



R Oct 01/14

BeforeConversion


550000Fig 412


RUDDER, ELEVATOR ANDTABS REPAIR G DENTON SANDWICH STRUCTURE

550000Fig 413


RUDDER, ELEVATOR AND TABS REPAIR H1 AND REPAIR H2 DENT ON SANDWICH STRUCTURE

550000Fig 414


RUDDER, ELEVATOR AND TABS REPAIR K NON PERFORATING DAMAGE

550000Fig 415


RUDDER, ELEVATOR AND TABS REPAIR L1 AND REPAIRL2 NON PERFORATINGDAMAGE OR DELAMINATION



HORIZONTAL STABILIZER SPAR BOX REPAIRS



REPAIR FOR LIGHT DAMAGESFOR RESIN FILLING



REPAIR FOR LIGHT DAMAGES BYRESIN FILLING AND EXTRA PLIES



HOT BOND REPAIR FOR NON-PERFORATING DAMAGE ON PANELEDGE CLOSE TO REAR SPAR



HOT BOND REPAIR FOR NON-PERFORATING DAMAGE ONTHE SKIN AT SPAR CAP


METAL PATCH REPAIR FORPERFORATING DAMAGE ON FRONT

SPAR CAP FIRST REPAIR SOLUTION551100Fig 405Config 2 (Refer to Repair

551100-300-812-A01)

METAL PATCH REPAIR FORPERFORATING DAMAGE ON FRONT SPARCAP SECOND REPAIR SOLUTION



METAL PATCH REPAIR FORPERFORATING DAMAGE ONTHE SKIN AT SPAR CAP



METAL PATCH REPAIR FOR FRONTAND REAR SPAR WEBS CUT OUT



REPAIR SCHEME FOR NON-PERFORATING DAMAGE ON THESKIN BETWEEN TWO SPARS



HOT BOND REPAIR FOR NON-PERFORATING DAMAGE ON THESKIN BETWEEN TWO SPARS



R Oct 01/14

BeforeConversion




METAL PATCH REPAIR FORNON-PERFORATING DAMAGEON THE SKIN AT SPAR CAP



REAR SPAR UPPER GROUNDINGSTRIP CORROSION REPAIR

551220Fig 401


HORIZONTAL STABILIZER LEADINGEDGE - RIB CRACK REPAIR (LH/RH)

552000Fig 401


RUDDER, ELEVATOR AND TABSCOMPOSITE PARTS REPAIRS

553100Fig 401


VERTICAL STABILIZER SPAR BOX



REAR SPAR GROUNDINGSTRIP CORROSION REPAIR



REPAIR FOR LIGHTDAMAGES BY RESIN FILLING



METAL PATCH REPAIR FORNON-PERFORATING DAMAGE ONSKIN BETWEEN TWO STRINGERS



HOT BOND REPAIR FOR NON-PERFORATING DAMAGE ON THESKIN BETWEEN TWO STRINGERS



METAL PATCH REPAIR FORPERFORATING DAMAGE ON

SKIN BETWEEN TWO STRINGERS



METAL PATCH REPAIR FORPERFORATING DAMAGE ATSKIN/STRINGERS LOCATION



REPAIR FOR LIGHT DAMAGES BYRESIN FILLING AND EXTRA PLIES



METAL PATCH REPAIR FOR FRONTAND REAR SPAR WEBS CUT OUT

553420Fig 401X


TEMPORARY REPAIR OF ASMALL CRACK ON FIN TIP RIB

554000Fig 401


RUDDER, ELEVATOR AND TABSCOMPOSITE PARTS REPAIRS

554100Fig 403


RUDDER SKIN REPAIR AT TABCOUNTERBALANCE ARM CUT OUT

CHAPTER 56



R Oct 01/14



561000Fig 301


FLIGHT COMPARTMENT

562100Fig 301


CABIN WINDOW - ALLOWABLE DAMAGES



560000Fig 401


WINDOWS GENERAL -COCKPIT WINDSHIELD ANDCABIN WINDOWS REPAIR

561000Fig 401


SPS - MAIN WINDSHIELDS(SPSATR42 111 OR SPSATR42211 OR SPSATR42122 OR

SPSATR422 22) ERODED AND/OR DEBONDED WEATHER SEAL REPAIR

561000Fig 402


PPG - MAIN WINDSHIELDS(NP-158801 3/4) ERODED AND/

OR DEBONDED MOISTURE SEAL REPAIR

561000Fig 403


PPG - MAIN WINDSHIELDS(NP-158801 1/2) ERODED AND/

OR DEBONDED MOISTURE SEAL REPAIR

561000Fig 404


PPG - FOWARD SIDE WINDOWS(NP-1588623/4) ERODED AND/ORDEBONDED MOISTURE SEAL REPAIR

CHAPTER 57



571200Fig 301


SPAR EXTRUSION

571200Fig 302


SPAR WEB

571210Fig 301


FRONT SPAR UPPER/LOWER CHORDSALLOWABLE DAMAGES ON VERTICAL

AND HORIZONTAL FLANGES

571210Fig 302

571210Table 301


FRONT SPAR TOP FLANGE ALLOWABLEDAMAGES ON STRIP SLAT



R Oct 01/14

BeforeConversion


571220Fig 301


REAR SPAR UPPER/LOWER CHORDSALLOWABLE DAMAGES ON VERTICAL

AND HORIZONTAL FLANGES


REAR SPAR TOP FLANGE ALLOWABLEDAMAGES ON STRIP SLAT571220

Fig 302 (Refer to Damages571220-200-803-A01)

REAR SPAR STRUCTURALDEFECT/DAMAGE REPORT

571300Fig 301


ALLOWABLE DAMAGES ON SHEET METALRIBS (WEB AND RIB FLANGES)

571410Fig 301


UPPER SURFACE SKIN

571412Fig 301


REMOVABLE PANELS - - ALLOWABLEBLENDING LIMITS OF HOUSINGSURFACE OF THE ACCESS DOOR

572200Fig 301


SPAR EXTRUSION

572200Fig 302


SPAR WEB

572300Fig 301


ALLOWABLE DAMAGES ON SHEET METALRIBS (WEB AND RIB FLANGES)

572400Fig 301


SKIN AND STIFFENERS - FUELOUTFLOW DEFLECTOR ANGLE

572410Fig 301


UPPER SURFACE SKINS REMOVABLE AND FIXED PANELS

573110Fig 301


WING TIP LIGHT TRANSPARENT COVER

574000Fig 301


COMPOSITE LEADING EDGE


Config 2


INBOARD FLAP STRUCTUREDEFINITION OF ZONES


Config 2


INBOARD FLAP STRUCTURESANDWICH CONSTRUCTIONZONE (FLAKING IMPACT)


Config 2


INBOARD FLAP STRUCTUREMONOLITH CONSTRUCTION ZONES5 AND 6 (FLAKING IMPACT)



R Oct 01/14

BeforeConversion



Config 2


INBOARD FLAP STRUCTURESANDWICH CONSTRUCTION

ZONE (SCORES, SCRATCHES)


Config 2


INBOARD FLAP STRUCTUREMONOLITH CONSTRUCTION ZONES5 AND 6 (SCORES, SCRATCHES)


Config 2


INBOARD FLAP STRUCTURE SANDWICHCONSTRUCTION ZONE (CRUSHING)


Config 2


INBOARD FLAP STRUCTURE(DELAMINATION)


Config 2


INBOARD FLAP STRUCTURE(SEPARATION - SKIN/CORE)


Config 2


INBOARD FLAP STRUCTURE(CHIPPING - SKIN/CORE)

575210Table 301Config1 and

Config 2


INBOARD FLAP STRUCTURE SUMMARY


Config 2


INBOARD FLAP STRUCTURE PICK-UPFITTINGS AND FITTINGS AT RIB 5



CAM GUIDE (WEAR)



CAM GUIDE (WEAR)



R Oct 01/14

BeforeConversion




CORROSION ON FLAP CAM GUIDES




575310Fig 301


OUTBOARD FLAP STRUCTURE- DEFINITION OF ZONES

575310Fig 302


OUTBOARD FLAP STRUCTURE- SANDWICH CONSTRUCTIONZONE (FLAKING IMPACT)

575310Fig 304


OUTBOARD FLAP STRUCTURE SANDWICHCONSTRUCTION ZONE (SCORES)

575310Fig 306


OUTBOARD FLAP STRUCTURE SANDWICHCONSTRUCTION ZONE (CRUSHING)

575310Fig 307


OUTBOARD FLAP STRUCTURE(DELAMINATION)

575310Fig 308


OUTBOARD FLAP STRUCTURE(SEPARATION - SKIN/CORE)


OUTBOARD FLAP STRUCTURE(CHIPPING - SKIN/CORE)575310

Fig 309 (Refer to Damages575310-200-808-A01)

OUTBOARD FLAP STRUCTURE SUMMARY

575310Fig 310


OUTBOARD FLAP STRUCTUREFITTINGS AT RIB 14 AND RIB 18

575320Fig 301CONFIG 1


CAM GUIDE (WEAR)



CAM GUIDE (WEAR)








COMPLETE STRUCTURE EVALUATION OF REPAIRABILITY576110

Fig. 301Config 1 (Refer to Damages

576110-200-802-A01)COMPLETE STRUCTURE AILERONBOX - DEFINITION OF ZONES

576110Fig. 301Config 2


COMPLETE STRUCTURE EVALUATION OF REPAIRABILITY



R Oct 01/14

BeforeConversion




COMPLETE STRUCTURE TAB DEFINITION OF ZONES



COMPLETE STRUCTURE HORN- DEFINITION OF ZONES



COMPLETE STRUCTURE AILERONBOX (SCORE/SCRATCH)



COMPLETE STRUCTURE AILERONBOX (PERFORATING IMPACT)



COMPLETE STRUCTUREAILERON BOX (FLAKING/

PERFORATING IMPACT OR NOT)



COMPLETE STRUCTURE AILERONBOX (DELAMINATION, SEPARATION)



COMPLETE STRUCTURETAB (SCORE/SCRATCH)



COMPLETE STRUCTURE TAB (FLAKING/PERFORATING IMPACT OR NOT)



COMPLETE STRUCTURE TAB(DELAMINATION, SEPARATION)



COMPLETE STRUCTUREHORN (SCORE, SCRATCH)



COMPLETE STRUCTUREHORN (FLAKING/

PERFORATING IMPACT OR NOT)



COMPLETE STRUCTURE HORN(DELAMINATION, SEPARATION)



COMPLETE STRUCTUREHORN (CRUSHING)



COMPLETE STRUCTURE SPRINGTAB SKIN PANEL (DELAMINATION)



COMPLETE STRUCTURE SPRING TABSKIN PANEL (SCORE, SCRATCH)



R Oct 01/14

BeforeConversion




COMPLETE STRUCTURE SPRINGTAB TRAILING EDGE (CRUSHING)



571210Fig 401X


FRONT SPAR - TEMPORARY REPAIRSCHEME FOR CRACK AND CORROSIONON LOWER AND UPPER SPAR FLANGES

571210Fig 401


FRONT SPAR - REPAIR SCHEMEFOR CRACK AND CORROSION ONLOWER AND UPPER SPAR FLANGES

571210Fig 402


FRONT SPAR REPAIR SCHEMEFOR CHAFING ON UPPERFRONT SPAR STRIP SLAT


FRONT SPAR LOWER STRIPREPAIR BETWEEN THE RIBS 10AND 11 (LH SIDE) REPAIR A


FRONT SPAR LOWER STRIPREPAIR BETWEEN THE RIBS 11AND 12 (LH SIDE) REPAIR B


FRONT SPAR LOWER STRIPREPAIR BETWEEN THE RIBS 10AND 11 (RH SIDE) REPAIR C

571210Fig 403


FRONT SPAR LOWER STRIPREPAIR BETWEEN THE RIBS 11AND 12 (RH SIDE) REPAIR D

571210Fig 404


FRONT SPAR LOWER STRIP BLENDOUT (LH/RH) BETWEEN THERIBS 10/11 AND RIBS 11/12

571220Fig 401X


REAR SPAR TEMPORARY REPAIRSCHEME FOR CRACK AND CORROSIONON LOWER AND UPPER SPAR FLANGES

571220Fig 401


REAR SPAR REPAIR SCHEMEFOR CRACK AND CORROSION ONLOWER AND UPPER SPAR FLANGES

571220Fig 402


REPAIR SCHEME FOR CHAFING ONUPPER REAR SPAR STRIP SLAT

571310Fig 401


RIBS STRUCTURE REPAIR SCHEMEFOR CRACK ON WING RIB FLANGE

(DAMAGE BETWEEN STIFF. 3 THRU 5)

571310Fig 402


RIBS STRUCTURE - REPAIR SCHEMEFOR CRACK ON WING RIB FLANGE




R Oct 01/14

BeforeConversion


571310Fig 403




571310Fig 404


RIBS STRUCTURE - REPAIR SCHEMEFOR CRACK ON WING RIB WEB

571410Fig 401


UPPER SURFACE SKIN REPAIR SCHEME FOR

CORROSION ON SKIN PANELS

571410Fig 402


UPPER SURFACE SKIN REPAIRSCHEME FOR CORROSION ON REMOVABLEPANELS BETWEEN RIB 0 AND RIB 8

571410Fig 403


REPAIR SCHEME FOR CORROSIONON REMOVABLE PANELS

BETWEEN RIB 8 AND RIB 13

571410Fig 404


UPPER SURFACE SKIN REPAIR SCHEME FOR CRACKON SKIN PANELS STIFFENERS

571412Fig 401


REMOVABLE PANELS REPAIRSCHEME FOR HOUSING SURFACE

ON THE ACCESS DOORS

571420Fig 401


LOWER SURFACE SKIN REPAIR SCHEMEFOR CRACK ON LOWER SURFACE PANELSTIFFENER DAMAGE (CRACK) CUT-OUT DEPTH 15 mm (0.591 in.) MAX.

571420Fig 402


LOWER SURFACE SKIN REPAIR SCHEMEFOR CRACK ON LOWER SURFACE PANELSTIFFENER DAMAGE (CRACK) CUT-OUT DEPTH 8mm (0.315 in.) MAX.

572200Fig 401


SPARS (FRONT AND REAR) REPAIR SCHEME FOR SPARWEB FLANGE RIB23 TO RIB30

572310Fig 401



572310Fig 402



572310Fig 403



572310Fig 404


RIBS STRUCTURE - REPAIR SCHEMEFOR CRACK ON WING RIB WEB

572400Fig 401X


SKINS AND STIFFENERS -TEMPORARY REPAIR FOR FUELOUTFLOW DEFLECTOR ANGLE

572400Fig 401


SKINS AND STIFFENERS - REPAIRFOR FUEL OUTFLOW DEFLECTOR ANGLE



R Oct 01/14

BeforeConversion


572411Fig 401


UPPER FIXED PANELS RIB 13 TORIB 23 - REPAIR SCHEME FORCRACK ON STIFFENERS BETWEENRIB 14 TO RIB 18 (CRACK

ON TWO SIDES OF STIFFENER)

572411Fig 402


UPPER FIXED PANELS RIB 13 TORIB 23 REPAIR SCHEME FORCRACK ON STIFFENERS BETWEENRIB 18 TO RIB 21 (CRACKON ONE SIDE AT STIFFENER)

572420Fig 401


LOWER SURFACE SKIN - REPAIRSCHEME FOR CRACK ON SKIN PANELAT RIB/STIFFENER INTERSECTION

572420Fig 401X


LOWER SURFACE SKIN - TEMPORARYREPAIR SCHEME FOR CRACKON SKIN PANEL AT RIB/STIFFENER INTERSECTION

572420Fig 402


LOWER SURFACE SKIN -REPAIR SCHEME FOR CRACKON SKIN PANEL RECESS

572420Fig 402X


LOWER SURFACE SKIN -TEMPORARY REPAIR SCHEME FORCRACK ON SKIN PANEL RECESS

572420Fig 403


LOWER SURFACE SKIN - REPAIRSCHEME FOR CRACK ON STIFFENERS

572420Fig 404


LOWER SURFACE SKIN -REPAIR SCHEME FOR CRACK ONSKIN PANEL AND STIFFENER

572420Fig 405


LOWER SURFACE SKIN - REPAIRSCHEME FOR CRACK ON SKIN

PANEL AND STIFFENER AT RIB/STIFFENER INTERSECTION


LEADING EDGES - REPAIRS574000Fig. 401 (Refer to Repair

574000-300-802-A01)LEADING EDGES - PLIES ON

KEVLAR FABRIC IDENTIFICATION

574000Fig. 402


LEADING EDGES - REPAIRFOR PICK-UP (SCHEME A)

574000Fig. 403


LEADING EDGES - REPAIR FORPUNCHING, NOTCH (SCHEME B)

574000Fig. 404


LEADING EDGES - REPAIRFOR SEPARATION (SCHEME C)

574000Fig. 405


LEADING EDGES - REPAIR FORINDENTATION ON SANDWICHSTRUCTURE (SCHEME D)



R Oct 01/14

BeforeConversion


574000Fig. 406


LEADING EDGE - REPAIRFOR PICK UP (SCHEME E)

574000Fig. 407


LEADING EDGES - REPAIR FORDELAMINATION (SCHEME F)

574000Fig. 408


LEADING EDGES - REPAIR FORPUNCHING, NOTCH (SCHEME H)

574310Fig. 401


COMPLETE STRUCTURE - REPAIRSCHEME FOR DELAMINATION

(BETWEEN RIB 20 AND RIB 21)

574310Fig. 402


COMPLETE STRUCTURE - REPAIRSCHEME FOR DELAMINATION

(BETWEEN RIB 21 AND RIB 22)

574310Fig. 403


COMPLETE STRUCTURE -REPAIR SCHEME FOR CORROSION(BETWEEN RIB 21 AND RIB 30)


INBOARD FLAP STRUCTURE - REPAIR575210Fig. 401Config 1

andConfig 2


INBOARD FLAP STRUCTURE- TEMPORARY REPAIR FOR

FLAKING, IMPACT ON SANDWICHCONSTRUCTION (SCHEME AX)


andConfig 2


INBOARD FLAP STRUCTURE -REPAIR FOR FLAKING, IMPACT ON

SANDWICH CONSTRUCTION (SCHEME A)


andConfig 2


INBOARD FLAP STRUCTURE -TEMPORARY REPAIR FOR FLAKING,PERFORATING IMPACT ON SANDWICH

CONSTRUCTION (SCHEME B1X)


andConfig 2


INBOARD FLAP STRUCTURE -TEMPORARY REPAIR FOR SCORES,

SCRATCHES ON SANDWICHCONSTRUCTION (SCHEME B1X)

575210Fig.405Config 1

andConfig 2


INBOARD FLAP STRUCTURE -TEMPORARY REPAIR FOR FLAKING,TRAVERSING IMPACT ON MONOLITHCONSTRUCTION (SCHEME B1X)


andConfig 2


INBOARD FLAP STRUCTURE -TEMPORARY REPAIR FOR SCORES,

SCRATCHES ON MONOLITHCONSTRUCTION (SCHEME B1X)



R Oct 01/14

BeforeConversion


575210Fig. 407

andConfig 2Config 1


INBOARD FLAP STRUCTURE -TEMPORARY REPAIR FOR FLAKINGON TRAILING EDGE ON SANDWICHCONSTRUCTION (SCHEME B1X)


andConfig 2


INBOARD FLAP STRUCTURE- REPAIR FOR FLAKING,

PERFORATING IMPACT ON SANDWICHCONSTRUCTION (SCHEME B1)


andConfig 2


INBOARD FLAP STRUCTURE -REPAIR FOR SCRATCHES, SCORES ONSANDWICH CONSTRUCTION (SCHEME B1)


andConfig 2


INBOARD FLAP STRUCTURE - REPAIRFOR FLAKING, TRAVERSING IMPACT ONMONOLITH CONSTRUCTION (SCHEME B1)


andConfig 2


INBOARD FLAP STRUCTURE -REPAIR FOR SCRATCHES, SCORES ONMONOLITH CONSTRUCTION (SCHEME B1)


andConfig 2


INBOARD FLAP STRUCTURE -REPAIR FOR FLAKING, IMPACT

ON TRAILING EDGES (SCHEME B1)


andConfig 2


INBOARD FLAP STRUCTURE - REPAIRFOR PERFORATING IMPACT ON

SANDWICH CONSTRUCTION (SCHEME B2)


andConfig 2


INBOARD FLAP STRUCTURE - REPAIRFOR NON-PERFORATING IMPACTOF 4 PLIES ZONE (SCHEME B3)


andConfig 2





R Oct 01/14

BeforeConversion



andConfig 2




andConfig 2


INBOARD FLAP STRUCTURE -REPAIR FOR IMPACT HOLE ON4 PLIES ZONE (SCHEME B4)


andConfig 2




andConfig 2




andConfig 2


INBOARD FLAP STRUCTURE - REPAIRFOR PERFORATING IMPACT ON

SANDWICH CONSTRUCTION SCHEME B5


andConfig 2




andConfig 2


INBOARD FLAP STRUCTURE -REPAIR FOR PERFORATING IMPACTON 6 PLIES ZONE (SCHEME B6)


andConfig 2




andConfig 2


INBOARD FLAP STRUCTURE -TEMPORARY REPAIR FOR FLAKING,TRAVERSING IMPACT ON MONOLITHCONSTRUCTION (SCHEME B7X)



R Oct 01/14

BeforeConversion



andConfig 2


INBOARD FLAP STRUCTURE -REPAIR FOR TRAVERSING IMPACT ONMONOLITH CONSTRUCTION (SCHEME B7)


andConfig 2


INBOARD FLAP STRUCTURE REPAIRFOR TRAVERSING IMPACT ONTRAILING EDGE (SCHEME B8)


andConfig 2


INBOARD FLAP STRUCTURE REPAIR FOR TRAVERSING IMPACT ONMONOLITH CONSTRUCTION (SCHEME B9)

575210Fi

Documents

introduccion al SRM ATR72